Abstract: A turbojet engine (2), such as an aircraft turbojet engine, comprising: an epicyclic gear train (36); a turbine rotating a transmission shaft (34) constrained to rotate with the inner planetary gear (60) of the epicyclic gear train (36); a fan (18) rigidly connected to the ring gear (66) of the epicyclic gear train (36); and an electric machine (70) comprising a rotor (72) and a stator (74), the rotor (72) being rigidly connected to the planet carrier (68) of the epicyclic gear train (36). Alternatively, the fan (18) is rigidly connected to the planet carrier and the electric machine (70) is rigidly connected to the ring gear. The invention also relates to methods for using said turbojet engine, in particular for controlling the reduction ratio between the transmission shaft and the turbine, in order to recover kinetic energy or for taxiing.

Abstract: The invention relates to a turbine engine (2), such as an aircraft turbofan engine, comprising: an epicyclic gear (36); a turbine driving in rotation a transmission shaft (34) integral in rotation with the sun gear (60) of the epicyclic gear (36); a fan (18) integral with the outer ring (66) of the epicyclic gear (36); and an electric motor (70) comprising a rotor (72) and a stator (74), the rotor (72) being integral with the planet carrier (68) of the epicyclic gear (36). Alternatively, the fan (18) is secured to the planet carrier and the electric motor (70) is secured to the outer ring. The invention also relates to methods of using said turbofan engine, in particular for regulating the reduction ratio between the shaft and the turbine, for recovering kinetic energy or for taxiing.